Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(arad20-il) ARA-D 20% AIRFOIL | Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 20% thick propeller airfoil Max thickness 20% at 25% chord Max camber 3.8% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (arad20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| arad20-il | 50,000 | 9 | 9.7 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 50,000 | 5 | 18.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad20-il | 100,000 | 9 | 24.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 100,000 | 5 | 38.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad20-il | 200,000 | 9 | 52 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 200,000 | 5 | 56.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad20-il | 500,000 | 9 | 79.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 500,000 | 5 | 80.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad20-il | 1,000,000 | 9 | 101.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 1,000,000 | 5 | 98.5 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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